Systems and methods providing airflow to a flight deck

ABSTRACT

Systems and methods provide airflow to a flight deck from a passenger entry area. The system includes a fan mounted within a door separating a flight deck from a passenger entry area. The fan is configured to direct airflow from the passenger entry area into the flight deck. The fan having a shield positioned adjacent to the passenger entry area that is configured to conceal the fan.

FIELD

Embodiments of the present disclosure generally relate to systems andmethods for pressurizing a flight deck.

BACKGROUND

Commercial aircraft typically includes a flight deck within a cockpit,from which pilots control the aircraft. During operation of theaircraft, situations can occur within the flight deck that may degradeair quality within the flight deck.

SUMMARY

Embodiments of the present disclosure generally relate to systems and/ormethods for pressurizing a flight deck to assure a positive pressuredifferential exists between the flight deck control volume and other airvolumes within the airplane to assure air that design air flow andleakage air flows are in the out direction from the flight deck toassure that no smoke or toxic gases penetrate the flight deck fromoutside the flight deck sources.

Commercial aircraft are typically partitioned into control volumes withmanaged air flows from higher pressure control volumes to lower pressurecontrol volumes. The flight deck from which pilots control the aircraftis one of these control volumes. During operation of the aircraft,situations can occur where air in a control volume may include smoke orother toxic gas.

A need exists for systems and/or methods for augmenting airflow into aflight deck of an aircraft to assure that the flight deck air pressureis maintained at a higher pressure to assure that out design air flowsand leakage air flows are in the out direction from the flight deck. Innormal operation the systems and/or methods are supplemental to the airmanagement system of the airplane. If there are failures in the airmanagement system of the airplane the systems and/or methods provideredundant pressurization for the flight deck.

With that need in mind, certain embodiments of the present disclosureprovide airflow into a flight deck, such as from a fan. The fan ismounted within a door separating a flight deck from a passenger entryarea. The passenger entry area correspond to a section of the aircraftrepresenting an area the passenger enters the aircraft. The fan isconfigured to direct airflow from the passenger entry area into theflight deck. For example, a rotation of blades of the fan are configuredto direct air from the passenger entry area into the flight deck. Thefan includes a shield positioned adjacent to the passenger entry areathat is configured to protect the fan from external projectiles.Optionally, the shield is a metal or one or more ceramic platesconfigured to absorb an impact or stop penetration of an externalprojectile into the fan.

In at least one embodiment, the airflow increases an air pressure withinthe flight deck. Optionally, the door includes a vent valve configuredto adjust the air pressure within the flight deck.

In at least one embodiment, the fan includes a filter interposed betweenthe shield and the fan within the door. The filter is configured toremove particles from the airflow. Optionally, the filter is a highefficiency particulate air filter (HEPA filter).

In at least one embodiment, the fan includes a light source configuredto indicate at least one of operation of the fan, a status of a filter,or a condition within the flight deck.

In at least one embodiment, the fan is operably coupled to anenvironmental control system (ECS). The fan is activated based oninstructions received from the ECS. Additionally or alternatively, theflight deck includes a user interface. The fan is activated based oninstructions received from the user interface.

In at least one embodiment, a second fan is mounted within the door. Thesecond fan is configured to direct airflow from the passenger entry areainto the flight deck. The shield is configured to extend to the secondfan and protect the second fan from external projectiles.

In at least one embodiment, the fan includes an elastomeric mount isconfigured to dampen sound emitted by the fan.

Certain embodiments of the present disclosure provide a method forproviding airflow into the flight deck. The method includes mounting afan within a door that separates a flight deck from a passenger entryarea, and coupling a shield to conceal the fan. The shield is positionedadjacent to the passenger entry area. The method includes directing anairflow from the passenger entry area into the flight deck.

Certain embodiments of the present disclosure provide an aircraft. Theaircraft includes an internal cabin. The internal cabin includes aflight deck and a passenger entry area. The internal cabin includes adoor separating the flight deck from the passenger entry area. The doorincludes a fan. The fan is configured to direct airflow from thepassenger entry area into the flight deck. The fan includes a shieldpositioned adjacent to the passenger entry area, which is configured toconceal the fan. The shield includes a metal or ceramic plate configuredto absorb an impact or stop penetration of an external projectile intothe fan. The fan includes a filter interposed between the shield and thefan. The filter is configured to remove particles from the airflow intothe flight deck. The aircraft includes an environmental control system(ECS) that is operably coupled to the fan.

BRIEF DESCRIPTION OF THE DRAWINGS

These and other features, aspects, and advantages of the presentdisclosure will become better understood when the following detaileddescription is read with reference to the accompanying drawings in whichlike numerals represent like parts throughout the drawings, wherein:

FIG. 1A illustrates an internal view of a portion of an internal cabinof an aircraft, according to an embodiment of the present disclosure;

FIG. 1B illustrates a lateral internal view of a cabin of an aircraft,according to an embodiment of the present disclosure;

FIG. 2A illustrate an exterior view of a door relative a passenger entryarea, according to an embodiment of the present disclosure;

FIG. 2B illustrates an interior view of a door relative to a flightdeck, according to an embodiment of the present disclosure;

FIG. 3 illustrates a front view of a rotor assembly of a fan relative toa passenger entry area, according to an embodiment of the presentdisclosure;

FIG. 4 illustrates a cross sectional view of a fan within a doorinterposed between a flight deck and a passenger entry area, accordingto an embodiment of the present disclosure;

FIG. 5 illustrates a flow chart of a method to provide airflow into aflight deck, according to an embodiment of the present disclosure;

FIG. 6 illustrates a front view of first and second fans within a doorinterposed between a flight deck and a passenger entry area, accordingto an embodiment of the present disclosure; and

FIG. 7 illustrates a perspective front view of an aircraft, according toan embodiment of the present disclosure.

DETAILED DESCRIPTION

The foregoing summary, as well as the following detailed description ofcertain embodiments will be better understood when read in conjunctionwith the appended drawings. As used herein, an element or step recitedin the singular and preceded by the word “a” or “an” should beunderstood as not necessarily excluding the plural of the elements orsteps. Further, references to “one embodiment” are not intended to beinterpreted as excluding the existence of additional embodiments thatalso incorporate the recited features. Moreover, unless explicitlystated to the contrary, embodiments “comprising” or “having” an elementor a plurality of elements having a particular property may includeadditional elements not having that property.

The embodiments herein describe a fan configured to provide airflow intoa flight deck of an aircraft. The fan is mounted within a door. The fanincludes a rotor assembly having a series of blades and a motor thatrotates the series of blades. The door separates the flight deck from apassenger entry area. The fan includes a rotating assembly with bladesconfigured to direct air from the passenger entry area into the flightdeck. The airflow provided by the fan increases an air pressure withinthe flight deck. For example, the airflow pushes air from the passengerentry area into the flight deck, which increases the pressure within theflight deck. The fan is configured to pressurize the flight deck toassure a positive pressure differential exists between the flight deckand other air volumes (e.g., passenger entry area) within the airplane.The positive pressure within the flight deck assures the air flow andleakage air flows are in the out direction from the flight deck toassure that no smoke or toxic gases penetrate the flight deck fromoutside the flight deck sources. The pressure within the flight deck maybe released via a vent valve positioned in the door. Optionally, thevent valve is triggered when an air pressure within the flight deck isabove a predetermined threshold. In response to the increased airpressure, the vent valve releases air from the flight deck into thepassenger entry area. As air is released from the flight deck, the airpressure within the flight deck is reduced.

In at least one embodiment, the fan includes a shield configured toobstruct external projectiles from damaging the fan from the passengerentry area. For example, the shield includes one or more metal orceramic plates that are overlaid on the fan at the passenger entry area.The metal and/or ceramic plates are configured to block the externalprojectile from entering the fan and/or absorb an impact and/or stoppenetration of an external projectile into the fan. Non-limitingexamples of the external projectile can be a bullet, a hardened ballpoint pen, a blade, a shank, and/or the like. The shield is positionedsuch that a gap is formed between the shield and the door. The gap isconfigured to allow air to enter through the gap and into the fan.

The fan may include a filter situated between the fan and the shield.The filter is configured to remove particles received from the airreceived from the passenger entry area. For example, the particles canrepresent dust, smoke, soot, fumes, pollen, bacteria, and/or the like.Optionally, the filter is configured to allow particles that have aparticular diameter, such as approximately 0.3 micrometers to enter thefan. For example, the filter may represent a high efficiency particulateair (HEPA) filter, which removes over 90% of particles from the air ofthe passenger entry area.

The fan may be activated based on instructions received from anenvironmental control system (ECS) or a user interface of the flightdeck. The instructions may include electrical energy, which providespower to the fan 204. Optionally, the instructions may represent abinary and/or analog signal configured to activate the fan 204. The ECSmay include a plurality of sensors positioned throughout the flight deckand the passenger entry area. For example, the ECS may include a sensorconfigured to detect smoke (e.g., optical sensor, ionization sensor,carbon monoxide sensor). In another example, the ECS may include one ormore sensors configured to detect particles hazardous to pilot healthsuch as sulfur oxide, ammonia, organic compounds, and the like. When theECS detects smoke and/or hazardous particles, the ECS activates the fan.Additionally or alternatively, the pilots may activate the fan manuallyusing a user interface.

Optionally, a plurality of fans are mounted within the door. Forexample, the door includes first and second fans. The second fan may beutilized to provide additional airflow based on the operation of thefirst fan.

FIG. 1A illustrate a view of a portion of an internal cabin 100 of anaircraft 108, according to an embodiment of the present disclosure. Theinternal cabin 100 of the aircraft 108 includes a flight deck 102 and apassenger entry area 104. The passenger entry area 104 corresponds to anarea proximate to a forward entry door 109. The internal cabin 100 ispartitioned into different control volumes with managed air flows frompressure control volumes. For example, the flight deck 102 from whichpilots control the aircraft is one of the control volumes. The forwardentry door 109 provides an entry way into the aircraft 108 forpassengers and/or crew. For example, the passenger entry area 104represents a region of the internal cabin 100 for passengers and/or crewto enter the aircraft 108 through the forward entry door 109. From thepassenger entry area 104, the passengers can proceed to a plurality ofseats 110. Alternatively, from the passenger entry area 104, the crewcan proceed into the flight deck 102, the galley, or other positionswithin the aircraft 108.

The flight deck 102 and the passenger entry area 104 are separated by apartition 106 and/or wall. The passenger entry area 104 represents atleast a portion of a passenger compartment. For example, the passengerentry area 104 includes a plurality of seats 110 for the passengers ofthe aircraft 108. The flight deck 102 includes an instrument panel (notshown) that enables the pilot to fly the aircraft 108. The instrumentpanel includes a user interface that receives inputs from the pilot toactivate different devices (e.g., a fan 204 shown in FIGS. 2-3). Theuser interface may include one or more devices for interacting with thepilot, such as: a keyboard, a mouse, a touchpad, one or more physicalbuttons, a touch screen, and the like.

FIG. 1B illustrates a lateral view of the internal cabin 100 of theaircraft 108, according to an embodiment of the present disclosure. Theinternal cabin 100 may also include a cargo hold 112. The cargo hold 112may extend over a portion of the aircraft 108.

The flight deck 102 includes an environmental control system (ECS) 114.The ECS 114 may include one or more sensors 116. During operation of theaircraft 108, situations can occur where air in the control volume ofthe flight deck 102 can include smoke or other toxic gas. The one ormore sensors 116 may measure an air pressure, detect smoke, detecthazardous fumes, abnormalities in the ambient air, and the like in theflight deck 102. The ECS 114 may be operably coupled to the instrumentpanel and/or other systems within the aircraft 108 (e.g., the fan 204shown in FIGS. 2-3).

FIG. 2A illustrates an exterior view of a door 202 as viewed from thepassenger entry area 104, according to an embodiment of the presentdisclosure. The partition 106 separates the flight deck 102 from thepassenger entry area 104. The partition 106 includes the door 202. Thedoor 202 includes a peephole 208 that allows a pilot to view thepassenger entry area 104 from the flight deck 102. As shown in FIG. 2A,the door 202 faces the passenger entry area 104.

FIG. 2A includes the fan 204 as viewed in the passenger entry area 104.The fan 204 is mounted within the door 202. For example, the fan 204 isrecessed relative to the surface area of the door 202 facing thepassenger entry area 104. The fan 204 may be recessed within the surfacearea of the door 202. A distance of the recess within the surface areaof the door 202 is based on a thickness of the fan 204 and clearancebetween the door 202 and the partition 106. For example, the recessenables the door 202 to open and be adjacent to the partition 106without being obstructed by the fan 204.

The fan 204 is shown having a shield 206. The shield 206 is positionedadjacent to the passenger entry area 104. The shield 206 conceals thefan 204 such that the fan 204 is not visible when viewed from thepassenger entry area 104. For example, the shield 206 blocks a line ofsight between blades of the fan 204, which prevents a passenger of thepassenger entry area 104 seeing into the flight deck 102. The shield 206is made of metal (e.g., steel, titanium), one or more ceramic plates(e.g., boron carbide, silicon carbide ceramic), or any such materialcapable of protecting the fan from an external projectile (e.g.,bulletproof, a hardened ball point pen, a blade, a shank) from thepassenger entry area 104. The shield 206 is configured to absorb animpact and/or stop penetration of an external projectile into the fan204. The shield 206 is configured to maintain an impervious separationbetween the flight deck 102 and the passenger entry area 104.

The shield 206 is positioned within the recess of the door 202. Aposition of the shield 206 relative to the surface area of the door 202is configured such that a gap forms between the surface area of the door202 and the shield 206. The shield 206 is coupled to the fan 204 suchthat the gap forms between the shield 206 and the door 202. Responsiveto activation of the fan 204, air flows through the gap and into the fan204 from the passenger entry area 104. For example, the gap allows airto flow into the fan 204 without the need for apertures and/or holesalong a surface of the shield 206.

FIG. 2B, illustrates an interior view of a door 202 as viewed fromflight deck 102, according to an embodiment of the present disclosure.The door 202 includes the fan 204 within the flight deck 102. The fan204 is mounted within the door 202, and can extend within the flightdeck 102.

FIG. 3 illustrates a front view of a rotor assembly 300 of the fan 204as seen from the passenger entry area 104. The shield 206 is shown beingtransparent to view the fan 204 behind the shield 206. The rotorassembly 300 has blades 302 that are angled to direct air from thepassenger entry area 104 into the flight deck 102. For example, when thefan 204 is activated, the blades 302 rotate to increase the pressure inthe flight deck 102 relative to the passenger compartment. The speed ofthe fan is adjustable (e.g., via the ECS) to control the air flow rate.

For example, the fan 204 rotates the blades such that air is propelledfrom the passenger entry area 104 into the fan 204 at approximately 2.28meters per second. Based on the rotation, the airflow from the fan 204is at approximately 1.8 meters per second. The airflow received from thefan 204 increases the air pressure within the flight deck 102 byapproximately 0.002 inches of water gauge (IWG) relative to thepassenger entry area 104. Additionally or alternatively, the fan 204 maybe rotated at a lesser or greater rate to push the air at a differentrate.

The fan 204 may include an external light source 304. The external lightsource 304 may be one or more light emitting diodes (LEDs), incandescentbulbs, compact fluorescent lamps, and the like. The external lightsource 304 is positioned along a surface area of the shield 206, suchthat the external light source 304 can be viewed from the passengerentry area 104. The external light source 304 is configured to indicatean operation of the fan 204, a status of the filter, a condition withinthe flight deck 102, or a combination thereof. The external light source304 can be activated by a control circuit 308, and/or the ECS 114.

For example, the external light source 304 is activated to indicate theoperation and/or activation of the fan 204. The fan 204 is activated bythe ECS 114, the user interface of the instrument panel, or the controlcircuit 308. The activation of the fan 204 is based on instructionsreceived from the ECS 114, the user interface, or the controller circuit308. The instructions may include electrical energy or an activationsignal (e.g., binary signal, analog signal), which activates the rotorassembly 300 to rotate the blades 302. Responsive to the activation ofthe rotor assembly 300, the external light source 304 is turned on toindicate the operation and/or activation of the fan 204.

In another example, the external light source 304 indicates a status ofa filter, such as when to replace the filter. The control circuit 308may be operably coupled to a memory that indicates an operational lifeof the filter. The operational life represents a length of time thefilter is effective without disrupting the operation of the fan 204. Forexample, over time particles are collected within the filter and candisrupt air entering the fan 204. The control circuit 308 is configuredto track an operational length of time the fan 204 is operating. Thecontrol circuit 308 compares the operational length with the operationallife of the filter. When the operational length is over the operationallife, the control circuit 308 instructs the external light source 304that indicates to replace the filter to activate.

Additionally or alternatively, the external light source 304 indicates acondition within the flight deck 102. For example, the fan 204 includesmultiple external light sources 304, each such that may correspond toconditions within the flight deck 102, such as fire, fumes, and/or thelike. The ECS 114 monitors the flight deck 102 and detects from thesensor array 116 (FIG. 1) when smoke and/or fumes are detected withinthe flight deck 102. For example, the ECS 114 sends instructions (e.g.,electrical energy, activation signal) to activate a first external lightsource 304 representing fire when the smoke is detected within theflight deck 102. In another example, the ECS 114 sends instructions toactivate a second external light source 304 representing fumes when thefumes are detected within the flight deck 102.

As used herein, the term “control circuit,” or the like may include anyprocessor-based or microprocessor-based system including systems usingmicrocontrollers, reduced instruction set computers (RISC), applicationspecific integrated circuits (ASICs), logic circuits, and any othercircuit or processor including hardware, software, or a combinationthereof capable of executing the functions described herein. Such areexemplary only, and are thus not intended to limit in any way thedefinition and/or meaning of such terms. For example, the controlcircuit 308 may be or include one or more processors that are configuredto control operation of the fan 204, as described above.

The control circuit 308 is configured to execute a set of instructionsthat are stored in one or more data storage units or elements (such asone or more memories), in order to process data. For example, thecontrol circuit 308 may include or be coupled to one or more memories.The data storage units may also store data or other information asdesired or needed. The data storage units may be in the form of aninformation source or a physical memory element within a processingmachine.

The set of instructions may include various commands that instruct thecontrol circuit 308 to perform specific operations such as the methodsand processes of the various embodiments of the subject matter describedherein. The set of instructions may be in the form of a softwareprogram. The software may be in various forms such as system software orapplication software. Further, the software may be in the form of acollection of separate programs, a program subset within a largerprogram or a portion of a program. The software may also include modularprogramming in the form of object-oriented programming. The processingof input data by the processing machine may be in response to usercommands, or in response to results of previous processing, or inresponse to a request made by another processing machine.

The diagrams of embodiments herein may illustrate one or more control orprocessing units. It is to be understood that the processing or controlunits may represent circuits, circuitry, or portions thereof that may beimplemented as hardware with associated instructions (e.g., softwarestored on a tangible and non-transitory computer readable storagemedium, such as a computer hard drive, ROM, RAM, or the like) thatperform the operations described herein. The hardware may include statemachine circuitry hardwired to perform the functions described herein.Optionally, the hardware may include electronic circuits that includeand/or are connected to one or more logic-based devices, such asmicroprocessors, processors, controllers, or the like. Optionally, theone or more control or processing units may represent processingcircuitry such as one or more of a field programmable gate array (FPGA),application specific integrated circuit (ASIC), microprocessor(s),and/or the like. The circuits in various embodiments may be configuredto execute one or more algorithms to perform functions described herein.The one or more algorithms may include aspects of embodiments disclosedherein, whether or not expressly identified in a flowchart or a method.

As used herein, the terms “software” and “firmware” are interchangeable,and include any computer program stored in a data storage unit (forexample, one or more memories) for execution by a computer, includingRAM memory, ROM memory, EPROM memory, EEPROM memory, and non-volatileRAM (NVRAM) memory. The above data storage unit types are exemplaryonly, and are thus not limiting as to the types of memory usable forstorage of a computer program.

FIG. 4 illustrates a cross sectional view of the fan 204 within the door202 (shown in FIG. 2) situated between the flight deck 102 and thepassenger entry area 104, according to an embodiment of the presentdisclosure. The fan 204 extends within the door 202. The fan 204 hasfasteners 408 that hold the shield 206 to the rotor assembly 300. Thefasteners 408 are positioned on a surface of the shield 206 and the fan204 at the flight deck 102. For example, the fasteners 408 extend from asurface of the fan 204 in the flight deck 102 to the shield 206. Thefasteners 408 are configured such that the fasteners 408 are accessiblefrom the flight deck 102. For example, the fasteners 408 are configuredsuch that the shield 206 is not able to be removed (e.g., unscrewed)from the passenger entry area 104. The fasteners 408 are configured suchthat the shield 206 can be removed when the fasteners 408 are removed(e.g., unscrewed) from the flight deck 102. Responsive to the fasteners408 being removed from the flight deck 102, provides access to a filter404 and/or the fan 204 at the passenger entry area 104. The fan 204 isshown sealed within the door using a plurality of seals 402. Forexample, the seals 402 are configured to hold the fan 204 at a positionwithin the door 202. Optionally, the seals 402 include silicone.

The fan 204 may include elastomeric mounts 406. The elastomeric mounts406 are configured to dampen sound emitted by the fan 204. For example,the elastomeric mounts 406 may be formed by rubber, silicon, polymer, orany suitable material that dampens vibration. During operation of thefan 204, the fan 204 oscillates at a set frequency (e.g., naturalfrequency). The elastomeric mounts 406 are configured to have aviscoelasticity at the set frequency, such that the elastomeric mounts406 absorb the oscillation of the fan 204. The absorption of theoscillation by the elastomeric mounts 406 reduces sound emitted from thefan 204 at the set frequency.

A gap 412 extends between the shield 206 and the door 202 in thepassenger entry area 104. For example, responsive to the shield 206being coupled to the fan 204 via the fasteners 408, the gap 412 isformed between the shield 206 and the door 202. The gap 412 allows airto flow into the fan 204 from the passenger entry area 104. For example,as the blades 302 rotate air is directed from the passenger entry area104 through the gap 412 and into the fan 204. The airflow from the fan204 is received at the flight deck 102, which increases an air pressurewithin the flight deck 102.

Optionally, air pressure within the flight deck 102 can be too highbased on the airflow from the fan 204. To reduce the air pressure, avent valve 410 can be positioned within the door 202. The vent valve 410can extend between the gaps 412, 414 through the door 202. The gap 414extends between the fan 204 and the door 202 in the flight deck 102. Thevent valve 410 is configured to adjust the air pressure within theflight deck 102 through the gaps 412, 414. For example, the airflowprovided by the fan 204 increases the air pressure within the flightdeck 102. As used herein, adjusting air pressure by the vent valve 410means decreasing the air pressure within the flight deck 102. The ventvalve 410 provides a channel for air to flow from the flight deck 102 atthe gap 414 into the passenger entry area 104 through the gap 412. Forexample, the airflow from the fan 204 creates an air pressuredifferential between the flight deck 102 and the passenger entry area104. The differential pushes air through the gap 414 from the flightdeck 102 and into the vent valve 410. The air is released through thegap 412 into the passenger entry area 104, which reduces the airpressure within the flight deck 102. Additionally or alternatively, thevent valve 410 may include a safety valve configured to obstruct thechannel of the vent valve 410 at the gap 414 until the air pressure ofthe flight deck 102 is above a predetermined threshold. For example, thepredetermined threshold may be the differential (e.g., at 0.05 IWG)between the flight deck 102 and the passenger entry area 104. Responsiveto the air pressure within the flight deck 102 being above thepredetermined threshold, the safety valve is released allowing air toflow within the vent valve 410.

FIG. 5 illustrates an embodiment of a flow chart of a method 500 toprovide airflow into the flight deck 102. The method 500, for example,may employ or be performed by structures or aspects of variousembodiments (e.g., systems and/or methods and/or process flows)discussed herein. In various embodiments, certain steps may be omittedor added, certain steps may be combined, certain steps may be performedconcurrently, certain steps may be split into multiple steps, or certainsteps may be performed in a different order.

Beginning at 502, the fan 204 is mounted within the door 202 thatseparates the flight deck 102 from the passenger entry area 104. Forexample, the fan 204 is mounted within the door 202 utilizing aplurality of seals 402. Optionally, the fan 204 is recessed relative tothe surface area of the door 202 facing the passenger entry area 104.

At 504, the shield 206 is coupled to at least one fan 204. For example,the shield 206 is positioned adjacent to the passenger entry area 104.The shield 206 is configured to cover a surface area of the fan 204 ofthe passenger entry area 104. The shield 206 blocks a line of sightbetween of the blades 302 of the fan 204, which prevents a passenger ofthe passenger entry area 104 seeing into the flight deck 102 through theshield 206. The shield 206 is further configured to absorb an impactand/or stop penetration of an external projectile into the fan 204.

At 506, one or more fans are activated based on instructions receivedfrom the ECS 114, the user interface, the control circuit 308. The ESC114 and the user interface are operably coupled to the fan 204. Forexample, the ECS 114 monitors the flight deck 102 and detects from thesensor array 116 when smoke and/or fumes are detected within the flightdeck 102. When ECS 114 detects smoke and/or fumes within the flight deck102, the ECS 114 sends instructions to activate the fan 204. In anotherexample, the user interface of the instrument panel receives a selectionfrom the pilot to activate the fan 204. The activation by the ESC 114and/or the user interface provides power to the fan 204, which rotatesthe blades 302 of the fan 204.

Alternatively, more than one fan is mounted within the door 202. FIG. 6illustrates a front view of first and second fans 204, 602 within thedoor 202 interposed between the flight deck 102 and the passenger entryarea 104, according to an embodiment of the present disclosure. Thesecond fan 602 is shown at a position adjacent to the first fan 204.Optionally, in other embodiments, other arrangements of the second fan602 relative to the first fan 204 are possible. For example, the firstfan 204 may be spaced apart from the second fan 602.

The shield 206 is shown expanded to be overlaid over the second fan 602.The shield 206 is configured to extend along a surface of the second fan602 of the passenger entry area 104. For example, the shield 206 isconfigured to cover a surface area of the second fan 602 of thepassenger entry area 104. The shield 206 blocks a line of sight betweenblades of the second fan 602, which prevents a passenger of thepassenger entry area 104 seeing into the flight deck 102. Additionally,the shield 206 is configured to absorb an impact and/or stop penetrationof an external projectile into the first and second fans 204, 602. Thegap 412 extends along the shield 206 between the first and second fans204, 602. For example, responsive to activation of the first and/orsecond fans 204, 602, airflows into the gap 412 from the passenger entryarea 104 into the first and/or second fans 204, 602, passenger entryarea

The second fan 602 can be utilized concurrently with the first fan 204.Optionally, the second fan 602 is activated when the first fan 204 failsand/or is not operational. For example, the ESC 114 activates the firstfan 204. The ESC 114 measures the air pressure before and afteractivation of the first fan 204. The ESC 114 compares the air pressurebefore and after the activation of the first fan 204 with apredetermined threshold. The predetermined threshold may represent apercentage and/or magnitude of change of the air pressure within theflight deck 102. When the air pressure after activation is below thepredetermined threshold, the ESC 114 activates the second fan 602.

At 508, sound emitted by at least one of the fans 204, 602 is dampenedby the elastomeric mount 406. For example, during operation of the fan204, the fan 204 oscillates at the set frequency. The elastomeric mounts406 are configured to have a viscoelasticity at the set frequency, suchthat the elastomeric mounts 406 absorb the oscillation and reduce soundemitted from the fan 204.

At 510, an airflow from the passenger entry area 104 is directed intothe flight deck 102. For example, the fan 204 rotates the blades 302such that air is propelled from the passenger entry area 104 into thefan 204. The air is exhausted within the flight deck 102 creating anairflow from the passenger entry area 104 into the flight deck 102.

At 512, the airflow from the passenger entry area 104 is filtered byremoving particles from the airflow into the flight deck 102. Forexample, the filter 404 represents a fibrous material that is configuredto block particles within the air from passing through the filter fromthe gap 412. The particles remain within the filter 404 as air passesthrough the filter 404.

At 514, air pressure from the flight deck 102 is released via the ventvalve 410 within the flight deck 102. For example, the airflow providedby the fan 204 increases the air pressure within the flight deck 102.The vent valve 410 provides a channel for air to flow from the flightdeck 102 into the passenger entry area 104. For example, the airflowcreates an air pressure differential between the flight deck 102 and thepassenger entry area 104. The differential pushes air from the flightdeck 102 through the vent valve 410 to the passenger entry area 104,which reduces the air pressure within the flight deck 102.

FIG. 7 illustrates a perspective front view of an aircraft, according toan embodiment of the present disclosure. The aircraft 108 includes apropulsion system 712 that may include two turbofan engines 714, forexample. Optionally, the propulsion system 712 may include more engines714 than shown. The engines 714 are carried by wings 716 of the aircraft108. In other embodiments, the engines 714 may be carried by a fuselage718 and/or an empennage 720. The empennage 720 may also supporthorizontal stabilizers 722 and a vertical stabilizer 724.

The fuselage 718 of the aircraft 108 defines an internal cabin, whichinclude a cockpit (e.g., flight deck 102), one or more work sections(for example, galleys, personnel carry-on baggage areas, and the like),one or more passenger sections (for example, first class, businessclass, and coach sections), and an aft section in which an aft rest areaassembly may be positioned. Each of the sections may be separated by acabin transition area, which may include one or more class/sectiondivider assemblies, as described herein.

Alternatively, instead of an aircraft, embodiments of the presentdisclosure may be used with various other vehicles, such as automobiles,buses, locomotives and train cars, sea craft, spacecraft, and the like.

As described above, embodiment of the present disclosure provide systemsand methods to retrofit an aircraft ventilation system to have a fanthat meets security requirements (e.g., the shield 206) and providebreathable air in a flight deck in the event of a fire.

While various spatial and directional terms, such as top, bottom, lower,mid, lateral, horizontal, vertical, front and the like may be used todescribe embodiments of the present disclosure, it is understood thatsuch terms are merely used with respect to the orientations shown in thedrawings. The orientations may be inverted, rotated, or otherwisechanged, such that an upper portion is a lower portion, and vice versa,horizontal becomes vertical, and the like.

As used herein, a structure, limitation, or element that is “configuredto” perform a task or operation is particularly structurally formed,constructed, or adapted in a manner corresponding to the task oroperation. For purposes of clarity and the avoidance of doubt, an objectthat is merely capable of being modified to perform the task oroperation is not “configured to” perform the task or operation as usedherein.

It is to be understood that the above description is intended to beillustrative, and not restrictive. For example, the above-describedembodiments (and/or aspects thereof) may be used in combination witheach other. In addition, many modifications may be made to adapt aparticular situation or material to the teachings of the variousembodiments of the disclosure without departing from their scope. Whilethe dimensions and types of materials described herein are intended todefine the parameters of the various embodiments of the disclosure, theembodiments are by no means limiting and are exemplary embodiments. Manyother embodiments will be apparent to those of skill in the art uponreviewing the above description. The scope of the various embodiments ofthe disclosure should, therefore, be determined with reference to theappended claims, along with the full scope of equivalents to which suchclaims are entitled. In the appended claims, the terms “including” and“in which” are used as the plain-English equivalents of the respectiveterms “comprising” and “wherein.” Moreover, the terms “first,” “second,”and “third,” etc. are used merely as labels, and are not intended toimpose numerical requirements on their objects. Further, the limitationsof the following claims are not written in means-plus-function formatand are not intended to be interpreted based on 35 U.S.C. § 112(f),unless and until such claim limitations expressly use the phrase “meansfor” followed by a statement of function void of further structure.

This written description uses examples to disclose the variousembodiments of the disclosure, including the best mode, and also toenable any person skilled in the art to practice the various embodimentsof the disclosure, including making and using any devices or systems andperforming any incorporated methods. The patentable scope of the variousembodiments of the disclosure is defined by the claims, and may includeother examples that occur to those skilled in the art. Such otherexamples are intended to be within the scope of the claims if theexamples have structural elements that do not differ from the literallanguage of the claims, or if the examples include equivalent structuralelements with insubstantial differences from the literal language of theclaims.

What is claimed is:
 1. A system for providing airflow into a flightdeck, the system comprising: a fan mounted within a door separating aflight deck from a passenger entry area, the fan being configured todirect airflow from the passenger entry area into the flight deck; and ashield positioned adjacent to the fan and facing the passenger entryarea, the shield configured to conceal the fan.
 2. The system of claim1, wherein the airflow increases an air pressure within the flight deck.3. The system of claim 2, wherein the door includes a vent valveconfigured to reduce the air pressure within the flight deck.
 4. Thesystem of claim 1, further comprising a filter situated between theshield and the fan within the door, the filter configured to removeparticles from the airflow.
 5. The system of claim 4, wherein the filteris a high efficiency particulate air (HEPA) type filter.
 6. The systemof claim 1, wherein the fan includes a light source configured toindicate at least one of operation of the fan, a status of a filter, ora condition within the flight deck.
 7. The system of claim 1, whereinthe fan is operably coupled to an environmental control system (ECS),the fan being configured to activate based on instructions received fromthe ECS.
 8. The system of claim 1, wherein the flight deck includes auser interface, the fan being configured to activate based oninstructions received from the user interface.
 9. The system of claim 1,further comprising a second fan mounted within the door configured todirect airflow from the passenger entry area into the flight deck,wherein the shield is configured to conceal both the first fan and thesecond fan.
 10. The system of claim 1, further comprising an elastomericmount configured to dampen sound emitted by the fan.
 11. The system ofclaim 1, wherein the shield is a metal or ceramic plate configured toabsorb an impact or stop penetration of an external projectile into thefan.
 12. A method for providing airflow into a flight deck, the methodcomprising: mounting a fan within a door that separates a flight deckfrom a passenger entry area, wherein the fan is coupled to a shieldpositioned adjacent to the passenger entry area, the fan beingconfigured to direct an airflow from the passenger entry area into theflight deck.
 13. The method of claim 12, wherein the directing operationincludes adjusting an air pressure within the flight deck.
 14. Themethod of claim 13, further comprising releasing air pressure from theflight deck via a vent valve positioned on the door.
 15. The method ofclaim 12, further comprising filtering the airflow from the passengerentry area by removing particles from the airflow into the flight deck.16. The method of claim 12, further comprising activating a light sourceconfigured to indicate at least one of operation of the fan, a status ofa filter, or a condition within the flight deck.
 17. The method of claim12, further comprising activating the fan based on instructions receivedfrom an environmental control system or a user interface.
 18. The methodof claim 12, further comprising activating a second fan mounted withinthe door to direct airflow from the passenger entry area into the flightdeck, wherein the shield is configured to conceal the second fan. 19.The method of claim 12, further comprising dampening sound emitted bythe fan by an elastomeric mount.
 20. An aircraft comprising: an internalcabin having a flight deck and a passenger entry area; a door separatingthe flight deck from the passenger entry area, wherein the doorcomprises a fan that is configured to direct airflow from the passengerentry area into the flight deck, the fan including a shield positionedadjacent to the passenger entry area that is configured to conceal thefan; an environmental control system (ECS) that is operably coupled tothe fan; wherein the shield includes a metal or ceramic plate configuredto absorb an impact or stop penetration of an external projectile intothe fan; and a filter interposed between the shield and the fan, thefilter configured to remove particles from the airflow into the flightdeck.